CN108216616B - High-efficient unmanned aerial vehicle automatically regulated rotor structure - Google Patents
High-efficient unmanned aerial vehicle automatically regulated rotor structure Download PDFInfo
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- CN108216616B CN108216616B CN201810062080.1A CN201810062080A CN108216616B CN 108216616 B CN108216616 B CN 108216616B CN 201810062080 A CN201810062080 A CN 201810062080A CN 108216616 B CN108216616 B CN 108216616B
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- 238000010276 construction Methods 0.000 claims description 2
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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Abstract
The invention relates to a high-efficiency automatic adjusting rotor wing structure of an unmanned aerial vehicle, which comprises a bearing base, a rotor wing, a driving mechanism, a rotary table mechanism, an air pipe and a control circuit, wherein the bearing base is of a rectangular plate-shaped structure, at least one positioning groove is formed in the bearing base, the tail end of the bearing base is mutually hinged with a body of the unmanned aerial vehicle through the rotary table structure, the air pipe is embedded in the positioning groove, the rotor wing and the driving mechanism are embedded in the air pipe, the driving mechanism is mutually connected with the air pipe through a positioning frame, and the control circuit is embedded in the bearing base and is respectively and electrically. The unmanned aerial vehicle equipment is simple in structure, flexible and convenient to use, high in operation automation degree, integration degree and modularization degree, and is beneficial to improving the convenience and reliability of assembly and disassembly of the unmanned aerial vehicle equipment and replacement of parts and the purposes of improving the bearing capacity of the unmanned aerial vehicle equipment and the stability, flexibility and reliability of flight control.
Description
Technical Field
The invention relates to an automatic adjusting rotor wing structure of a high-efficiency unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles.
Background
At present, rotor type unmanned aerial vehicle is one of the main forms in current unmanned aerial vehicle structure, the use amount is huge, but discover in the in-service use, current rotor type unmanned aerial vehicle's rotor mechanism often all with unmanned aerial vehicle organism formula structure as an organic whole, although can satisfy the needs of using, but lead to current rotor type unmanned aerial vehicle in service to have rotor mechanism installation, dismantle and change the operation flexibility poor, the flexibility of rotor type unmanned aerial vehicle equipment operation use has seriously been influenced, also cause current rotor type unmanned aerial vehicle equipment in service simultaneously, rotor equipment in service produced drive power size, direction control and regulation flexibility are relatively poor and the control range is narrow, on the one hand, unmanned aerial vehicle rotor power performance and operating efficiency are relatively poor seriously influenced, and cause the operation energy consumption to increase, on the other hand also leads to current unmanned aerial vehicle equipment operation flexibility, the utility model discloses a, Reliability and flight stability homogeneous phase are relatively poor, to this problem, the urgent need develops a brand-new unmanned aerial vehicle rotor structure to satisfy the needs of in-service use.
Disclosure of Invention
The invention aims to overcome the defects and provide the automatic adjusting rotor wing structure of the high-efficiency unmanned aerial vehicle.
In order to realize the purpose, the invention is realized by the following technical scheme:
an automatic adjusting rotor wing structure of a high-efficiency unmanned aerial vehicle comprises a bearing base, rotor wings, a driving mechanism, a rotary table mechanism, an air pipe and a control circuit, wherein the bearing base is of a rectangular plate-shaped structure, at least one positioning groove is formed in the bearing base, the positioning grooves are uniformly distributed along the axial direction of the bearing base, the axial line of each positioning groove is perpendicular to and intersected with the axial line of the bearing base, the tail end of the bearing base is hinged with a body of the unmanned aerial vehicle through the rotary table structure, the axial line of the bearing base is intersected with the axial line of the body of the unmanned aerial vehicle and forms an included angle of 0-180 degrees, the air pipe is embedded in the positioning grooves and is hinged with the side walls of the positioning grooves through at least two rotary table mechanisms, the axial line of the air pipe and the lower surface of the bearing base form an included angle of 30-90 degrees, the driving mechanism is connected with the air pipe through the positioning frame, and the control circuit is embedded in the bearing base and is respectively electrically connected with the driving mechanism and the rotary table mechanism.
Furthermore, the cross section of the bearing base is in any one of a shuttle-shaped structure and a water drop-shaped structure.
Further, bear the base and be airtight cavity structures, including bearing fossil fragments, protective housing and inside lining wall, the fossil fragments that bear be frame construction, the protective housing cladding at bear the fossil fragments surface, the inside lining wall cladding at bearing the fossil fragments internal surface, protective housing and inside lining wall between constitute inclosed cushion chamber, the inside lining wall constitute airtight structure's the chamber that bears.
Furthermore, the cushion chamber in establish the elasticity bed course, the bearing chamber in establish at least one booster pump, booster pump one end move the air duct and be connected with the tuber pipe lateral wall, the booster pump other end through at least one air duct with bear the weight of base upper surface intercommunication, just bear a plurality of thru holes of base upper surface equipartition, each thru hole all communicates with each other with the air duct.
Further, the tuber pipe include that the body bears body, guide plate and nozzle, wherein the body that bears be hollow tubular structure, bear body up end and lower terminal surface department and all establish a plurality of guide plates, the guide plate pass through rotary table mechanism and bear the internal surface of body articulated, just guide plate and bear the body axis and be 0-90 contained angle, and the interval is 1/6-1/3 for bearing the body diameter between two adjacent guide plates, the nozzle at least two, inlay in bearing the body lateral wall, and each nozzle encircles and bears the body axis equipartition to be 0-90 contained angle with bearing the body axis, the nozzle between each other parallel and through control valve and air duct intercommunication.
Furthermore, the cross section of the bearing pipe body is any one of a rectangular structure and an isosceles trapezoid structure.
Further, the driving mechanism is any one of an electric motor and an internal combustion engine.
Furthermore, the turntable mechanism is a three-dimensional turntable, and the turntable mechanism is provided with an angle sensor which is electrically connected with the control circuit.
Further, control circuit include data processing module, data communication module, data bus module, data communication terminal, wireless data communication antenna and drive module, data bus module respectively with data processing module, data communication module and drive module electrical connection, data communication module and data communication terminal, wireless data communication antenna electrical connection to through data communication terminal, wireless data communication antenna and unmanned aerial vehicle operating system electrical connection, drive module respectively with actuating mechanism, revolving stage mechanism electrical connection.
The unmanned aerial vehicle rotor wing system is simple in structure, flexible and convenient to use, high in operation automation degree, integration degree and modularization degree, capable of effectively improving the installation and positioning flexibility of the unmanned aerial vehicle rotor wing and the strength of a bearing structure and facilitating improvement of convenience and reliability of assembly, disassembly and part replacement of the unmanned aerial vehicle, and capable of effectively improving the power performance of the unmanned aerial vehicle rotor wing system and the flexibility and reliability of driving power regulation control, so that the purposes of improving the bearing capacity and flight control stability, flexibility and reliability of unmanned aerial vehicle equipment operation are achieved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
fig. 2 is a schematic diagram of a control circuit structure.
Detailed Description
As shown in fig. 1 and 2, an efficient automatic adjusting rotor structure of an unmanned aerial vehicle comprises a bearing base 1, a rotor 2, a driving mechanism 3, a turntable mechanism 4, an air pipe 5 and a control circuit 6, wherein the bearing base 1 is a rectangular plate-shaped structure, the bearing base 1 is provided with at least one positioning groove 7, the positioning grooves 7 are uniformly distributed along the axis direction of the bearing base 1, the axes of the positioning grooves 7 are perpendicular to and intersected with the axis of the bearing base 1, the tail end of the bearing base 1 is hinged with an unmanned aerial vehicle body 8 through the turntable structure 4, the axis of the bearing base 1 is intersected with the axis of the unmanned aerial vehicle body 8 and forms an included angle of 0-180 degrees, the air pipe 5 is embedded in the positioning groove 7 and is hinged with the side wall of the positioning groove 7 through at least two turntable mechanisms 4, the axis of the air pipe 5 and the lower surface of the bearing base 1 form an included angle of 30-90 degrees, the rotor 2 and the driving mechanism 3 are both embedded in, rotor 2, actuating mechanism 3 all distribute with tuber pipe 5 is coaxial, and actuating mechanism 3 passes through locating rack 10 and tuber pipe 5 interconnect, and control circuit 6 inlays in bearing base 1 to respectively with actuating mechanism 3, 4 electrical connection of revolving stage mechanism.
In this embodiment, the cross section of the supporting base 1 is any one of a shuttle structure and a water drop structure.
In this embodiment, the bearing base 1 is a closed cavity structure, and includes a bearing keel 101, a protective shell 102 and a lining wall 103, the bearing keel 101 is a frame structure, the protective shell 102 is coated on the outer surface of the bearing keel 101, the lining wall 103 is coated on the inner surface of the bearing keel 101, a closed buffer cavity 104 is formed between the protective shell 102 and the lining wall 103, and the lining wall 103 forms a bearing cavity 105 of the closed structure.
In this embodiment, the cushion chamber 104 is internally provided with an elastic cushion layer 11, the bearing chamber 105 is internally provided with at least one booster pump 12, one end of the booster pump 12 is connected with the side wall of the air duct 5 through an air duct 13, the other end of the booster pump 12 is communicated with the upper surface of the bearing base 1 through at least one air duct 13, the upper surface of the bearing base 1 is uniformly provided with a plurality of through holes 14, and each through hole 14 is communicated with the air duct 13.
In this embodiment, the air duct 5 includes a duct body 51, a plurality of flow deflectors 52 and nozzles 53, wherein the duct body 51 is a hollow tubular structure, the upper end surface and the lower end surface of the duct body 51 are provided with the plurality of flow deflectors 52, the flow deflectors 52 are hinged to the inner surface of the duct body 51 through the turntable mechanism 4, the flow deflectors 52 and the axis of the duct body 51 form an included angle of 0 ° to 90 °, the distance between two adjacent flow deflectors 52 is 1/6 to 1/3 of the diameter of the duct body 51, at least two nozzles 53 are embedded in the side wall of the duct body 51, the nozzle rings 53 are uniformly distributed around the axis of the duct body 51 and form an included angle of 0 ° to 90 ° with the axis of the duct body 51, and the nozzles 53 are mutually connected in parallel and are communicated with the air duct 13 through the control valve 15.
In this embodiment, the cross section of the bearing pipe 51 is any one of a rectangular structure and an isosceles trapezoid structure.
In the present embodiment, the drive mechanism 3 is either an electric motor or an internal combustion engine.
In this embodiment, the turntable mechanism 4 is a three-dimensional turntable, and the angle sensor 15 is arranged on the turntable mechanism 4, and the angle sensor 15 is electrically connected with the control circuit 6.
In this embodiment, the control circuit 6 includes a data processing module, a data communication module, a data bus module, a data communication terminal 61, a wireless data communication antenna 62 and a driving module, the data bus module is electrically connected with the data processing module, the data communication module and the driving module respectively, the data communication module is electrically connected with the data communication terminal 61 and the wireless data communication antenna 62 and is electrically connected with the unmanned aerial vehicle operation system through the data communication terminal 61 and the wireless data communication antenna 62, and the driving module is electrically connected with the driving mechanism 3 and the turntable mechanism 4 respectively.
The unmanned aerial vehicle rotor wing system is simple in structure, flexible and convenient to use, high in operation automation degree, integration degree and modularization degree, capable of effectively improving the installation and positioning flexibility of the unmanned aerial vehicle rotor wing and the strength of a bearing structure and facilitating improvement of convenience and reliability of assembly, disassembly and part replacement of the unmanned aerial vehicle, and capable of effectively improving the power performance of the unmanned aerial vehicle rotor wing system and the flexibility and reliability of driving power regulation control, so that the purposes of improving the bearing capacity and flight control stability, flexibility and reliability of unmanned aerial vehicle equipment operation are achieved.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (9)
1. The utility model provides a high-efficient unmanned aerial vehicle automatically regulated rotor structure, a serial communication port, high-efficient unmanned aerial vehicle automatically regulated rotor structure including bearing base, rotor, actuating mechanism, revolving stage mechanism, tuber pipe and control circuit, bearing base be rectangle platelike structure, bearing base on establish at least one constant head tank, the constant head tank along bearing base axis direction equipartition, just constant head tank axis perpendicular and crossing with bearing base axis, bearing base end articulated each other through revolving stage structure and unmanned aerial vehicle fuselage, just bearing base axis and unmanned aerial vehicle fuselage axis intersect and be 0-180 contained angle, the tuber pipe inlay in the constant head tank to articulate through two at least revolving stage mechanisms with the constant head tank lateral wall, just tuber pipe axis and bearing base lower surface be 30-90 contained angles, rotor, actuating mechanism all inlays in the tuber pipe, wherein the rotor be located actuating mechanism directly over and through transmission shaft and actuating mechanism interconnect, rotor, actuating mechanism all with the coaxial distribution of tuber pipe, actuating mechanism pass through locating rack and tuber pipe interconnect, control circuit inlay in bearing the weight of the base to respectively with actuating mechanism, revolving stage mechanism electrical connection.
2. The high efficiency unmanned aerial vehicle self-adjusting rotor structure of claim 1, wherein: the cross section of the bearing base is in any one of a fusiform structure and a water drop type structure.
3. The high efficiency unmanned aerial vehicle self-adjusting rotor structure of claim 1, wherein: bear the base and be airtight cavity structures, including bearing fossil fragments, protective housing and inside lining wall, the keel that bears be frame construction, the protective housing cladding at bear the keel surface, the inside lining wall cladding at bear the keel internal surface, protective housing and inside lining wall between constitute inclosed cushion chamber, the inside lining wall constitute airtight cavity structures's the chamber that bears.
4. The high efficiency unmanned aerial vehicle self-adjusting rotor structure of claim 3, wherein: the buffer cavity in be equipped with the elastic cushion layer, the bearing cavity in establish at least one booster pump, booster pump one end pass through the air duct and be connected with the tuber pipe lateral wall, the booster pump other end pass through at least one air duct and bear the weight of base upper surface intercommunication, just bear a plurality of thru holes of base upper surface equipartition, each thru hole all communicates with each other with the air duct.
5. The high efficiency unmanned aerial vehicle self-adjusting rotor structure of claim 1, wherein: the tuber pipe including bearing body, guide plate and nozzle, wherein the body of bearing be hollow tubular structure, bear body up end and lower terminal surface department and all establish a plurality of guide plates, the guide plate pass through revolving stage mechanism and bear the weight of body internal surface articulated, just guide plate and bear the weight of body axis and be 0-90 contained angle, and the interval is 1/6-1/3 for bearing the weight of body diameter between two adjacent guide plates, the nozzle at least two, inlay in bearing the weight of the body lateral wall, and each nozzle encircles and bears the weight of body axis equipartition to be 0-90 contained angle with bearing the weight of body axis, the nozzle between each other parallel and through control valve and air duct intercommunication.
6. The high efficiency unmanned aerial vehicle self-adjusting rotor structure of claim 5, wherein: the cross section of the bearing pipe body is any one of a rectangular structure and an isosceles trapezoid structure.
7. The high efficiency unmanned aerial vehicle self-adjusting rotor structure of claim 1, wherein: the driving mechanism is any one of an electric motor and an internal combustion engine.
8. The high efficiency unmanned aerial vehicle self-adjusting rotor structure of claim 1, wherein: the rotary table mechanism is a three-dimensional rotary table, an angle sensor is arranged on the rotary table mechanism, and the angle sensor is electrically connected with the control circuit.
9. The high efficiency unmanned aerial vehicle self-adjusting rotor structure of claim 1, wherein: the control circuit comprises a data processing module, a data communication module, a data bus module, a data communication terminal, a wireless data communication antenna and a driving module, wherein the data bus module is electrically connected with the data processing module, the data communication module and the driving module respectively, the data communication module is electrically connected with the data communication terminal and the wireless data communication antenna and is electrically connected with an unmanned aerial vehicle running system through the data communication terminal and the wireless data communication antenna, and the driving module is electrically connected with a driving mechanism and a turntable mechanism respectively.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810062080.1A CN108216616B (en) | 2018-01-23 | 2018-01-23 | High-efficient unmanned aerial vehicle automatically regulated rotor structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810062080.1A CN108216616B (en) | 2018-01-23 | 2018-01-23 | High-efficient unmanned aerial vehicle automatically regulated rotor structure |
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| CN108216616A CN108216616A (en) | 2018-06-29 |
| CN108216616B true CN108216616B (en) | 2021-03-30 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109110121A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of novel three rotor wing unmanned aerial vehicles structure |
| CN109110120A (en) * | 2018-09-07 | 2019-01-01 | 佛山皖和新能源科技有限公司 | A kind of three rotor wing unmanned aerial vehicle lift systems |
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|---|---|---|---|---|
| CN102105357A (en) * | 2008-05-30 | 2011-06-22 | 吉洛工业有限公司 | A flying machine comprising twin contra-rotating vertical axis propellers |
| CN105882959A (en) * | 2015-02-13 | 2016-08-24 | 空中客车防卫和太空有限责任公司 | Aircraft capable of vertical takeoff |
| CN106628161A (en) * | 2017-01-17 | 2017-05-10 | 深圳市哈威飞行科技有限公司 | Rapidly-disassembled duct structure |
| CN107117297A (en) * | 2017-05-06 | 2017-09-01 | 安徽省先胜农业发展有限公司 | A kind of multi-rotor aerocraft for pesticide spraying |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140231582A1 (en) * | 2012-10-03 | 2014-08-21 | Sean Headrick | Methods and Systems of Constructing a Multi Rotor Aircraft Fuselage |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102105357A (en) * | 2008-05-30 | 2011-06-22 | 吉洛工业有限公司 | A flying machine comprising twin contra-rotating vertical axis propellers |
| CN105882959A (en) * | 2015-02-13 | 2016-08-24 | 空中客车防卫和太空有限责任公司 | Aircraft capable of vertical takeoff |
| CN106628161A (en) * | 2017-01-17 | 2017-05-10 | 深圳市哈威飞行科技有限公司 | Rapidly-disassembled duct structure |
| CN107117297A (en) * | 2017-05-06 | 2017-09-01 | 安徽省先胜农业发展有限公司 | A kind of multi-rotor aerocraft for pesticide spraying |
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| CN108216616A (en) | 2018-06-29 |
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